4.7x4.2E (47x42E.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.5000 4.2500 0.0000 0.0000 0.2500 0.0000 0.1343 0.0000 0.0672 0.0000 0.0500 0.0000 0.0000 0.0600 0.4794 4.2500 0.0095 -0.1498 0.2469 0.0088 0.1322 1.4404 0.0634 0.0634 0.0574 0.0059 -0.0191 0.1200 0.4566 4.2500 0.0738 -0.2882 0.2437 0.0324 0.1302 5.5898 0.0594 0.0670 0.0770 0.0153 -0.0100 0.1800 0.4369 4.2500 0.2419 -0.3526 0.2406 0.0667 0.1282 12.0708 0.0560 0.0671 0.1032 0.0270 0.0039 0.2400 0.4260 4.2500 0.5556 -0.2718 0.2377 0.1079 0.1264 20.2268 0.0538 0.0634 0.1343 0.0399 0.0215 0.3000 0.4271 4.2500 1.0436 0.0117 0.2352 0.1521 0.1246 28.9702 0.0532 0.0574 0.1693 0.0528 0.0418 0.3600 0.4398 4.2500 1.7066 0.5312 0.2333 0.1957 0.1230 37.0336 0.0541 0.0504 0.2058 0.0648 0.0640 0.4200 0.4596 4.2500 2.4981 1.2727 0.2319 0.2348 0.1214 43.4299 0.0558 0.0434 0.2402 0.0751 0.0867 0.4800 0.4801 4.2500 3.3064 2.1479 0.2314 0.2658 0.1199 47.6309 0.0576 0.0370 0.2687 0.0828 0.1084 0.5400 0.4953 4.2500 3.9562 2.9781 0.2318 0.2848 0.1185 49.3830 0.0587 0.0315 0.2866 0.0873 0.1268 0.6000 0.5004 4.2500 4.2474 3.5016 0.2333 0.2880 0.1172 48.4080 0.0587 0.0271 0.2898 0.0870 0.1387 0.6597 0.4977 4.2500 4.2500 3.7156 0.2352 0.2798 0.1160 45.7147 0.0577 0.0236 0.2818 0.0836 0.1440 0.7150 0.4933 4.2500 4.2500 3.8520 0.2367 0.2710 0.1150 43.4095 0.0567 0.0208 0.2732 0.0815 0.1467 0.7701 0.4884 4.2500 4.2500 3.9526 0.2377 0.2611 0.1140 41.2946 0.0557 0.0185 0.2636 0.0800 0.1470 0.8251 0.4832 4.2500 4.2500 4.0248 0.2383 0.2501 0.1130 39.3435 0.0546 0.0167 0.2529 0.0789 0.1449 0.8802 0.4777 4.2500 4.2500 4.0710 0.2386 0.2380 0.1120 37.5421 0.0535 0.0154 0.2411 0.0779 0.1403 0.9352 0.4718 4.2500 4.2500 4.0925 0.2385 0.2250 0.1110 35.8769 0.0524 0.0146 0.2284 0.0770 0.1336 0.9903 0.4655 4.2500 4.2500 4.0966 0.2380 0.2122 0.1100 34.3355 0.0512 0.0141 0.2159 0.0759 0.1261 1.0453 0.4589 4.2500 4.2500 4.0999 0.2372 0.1995 0.1090 32.9067 0.0500 0.0136 0.2036 0.0750 0.1184 1.1003 0.4519 4.2500 4.2500 4.1034 0.2360 0.1871 0.1080 31.5800 0.0488 0.0131 0.1916 0.0740 0.1107 1.1554 0.4446 4.2500 4.2500 4.1072 0.2345 0.1750 0.1070 30.3463 0.0476 0.0126 0.1798 0.0732 0.1030 1.2104 0.4369 4.2500 4.2500 4.1112 0.2326 0.1632 0.1061 29.1972 0.0463 0.0121 0.1682 0.0723 0.0954 1.2655 0.4288 4.2500 4.2500 4.1157 0.2304 0.1516 0.1051 28.1249 0.0451 0.0116 0.1569 0.0713 0.0877 1.3205 0.4204 4.2500 4.2500 4.1206 0.2278 0.1402 0.1041 27.1229 0.0438 0.0111 0.1459 0.0704 0.0801 1.3756 0.4117 4.2500 4.2500 4.1261 0.2249 0.1292 0.1031 26.1849 0.0424 0.0106 0.1350 0.0694 0.0726 1.4306 0.4025 4.2500 4.2500 4.1320 0.2217 0.1184 0.1021 25.3054 0.0411 0.0101 0.1244 0.0683 0.0652 1.4856 0.3931 4.2500 4.2500 4.1386 0.2182 0.1078 0.1011 24.4796 0.0397 0.0095 0.1141 0.0672 0.0578 1.5407 0.3832 4.2500 4.2500 4.1455 0.2143 0.0975 0.1001 23.7029 0.0384 0.0090 0.1040 0.0658 0.0505 1.5957 0.3730 4.2500 4.2500 4.1520 0.2102 0.0874 0.0991 22.9714 0.0370 0.0086 0.0941 0.0638 0.0428 1.6508 0.3625 4.2500 4.2500 4.1576 0.2057 0.0775 0.0981 22.2815 0.0356 0.0082 0.0845 0.0615 0.0350 1.7058 0.3516 4.2500 4.2500 4.1613 0.2010 0.0677 0.0971 21.6298 0.0341 0.0079 0.0751 0.0588 0.0271 1.7609 0.3403 4.2500 4.2500 4.1610 0.1959 0.0582 0.0961 21.0135 0.0327 0.0075 0.0660 0.0559 0.0194 1.8159 0.3287 4.2500 4.2500 4.1569 0.1906 0.0490 0.0951 20.4299 0.0313 0.0072 0.0571 0.0531 0.0118 1.8709 0.3167 4.2500 4.2500 4.1509 0.1849 0.0401 0.0941 19.8766 0.0298 0.0068 0.0485 0.0503 0.0044 1.9260 0.3044 4.2500 4.2500 4.1438 0.1790 0.0314 0.0931 19.3513 0.0283 0.0065 0.0400 0.0477 -0.0025 1.9810 0.2917 4.2500 4.2500 4.1371 0.1728 0.0231 0.0921 18.8521 0.0269 0.0061 0.0319 0.0453 -0.0091 2.0361 0.2786 4.2500 4.2500 4.1318 0.1664 0.0152 0.0911 18.3771 0.0254 0.0056 0.0240 0.0431 -0.0153 2.0911 0.2652 4.2500 4.2500 4.1298 0.1597 0.0076 0.0902 17.9247 0.0239 0.0052 0.0163 0.0412 -0.0210 2.1462 0.2514 4.2500 4.2500 4.1325 0.1527 0.0004 0.0892 17.4933 0.0224 0.0047 0.0088 0.0394 -0.0263 2.2012 0.2373 4.2500 4.2500 4.1411 0.1455 -0.0065 0.0882 17.0817 0.0209 0.0042 0.0016 0.0378 -0.0311 2.2540 0.2210 4.2500 4.2500 4.1537 0.1360 -0.0134 0.0872 16.7041 0.0193 0.0036 -0.0058 0.0350 -0.0359 2.2682 0.2137 4.2500 4.2500 4.1576 0.1306 -0.0161 0.0870 16.6050 0.0186 0.0034 -0.0087 0.0328 -0.0377 2.2802 0.2060 4.2500 4.2500 4.1609 0.1247 -0.0187 0.0867 16.5224 0.0179 0.0031 -0.0116 0.0302 -0.0395 2.2922 0.1968 4.2500 4.2500 4.1701 0.1173 -0.0218 0.0865 16.4406 0.0170 0.0029 -0.0149 0.0268 -0.0415 2.3042 0.1859 4.2500 4.2500 4.1823 0.1082 -0.0253 0.0863 16.3596 0.0160 0.0025 -0.0188 0.0225 -0.0439 2.3162 0.1726 4.2500 4.2500 4.1991 0.0969 -0.0294 0.0861 16.2794 0.0149 0.0022 -0.0234 0.0171 -0.0466 2.3282 0.1562 4.2500 4.2500 4.2237 0.0825 -0.0343 0.0859 16.2000 0.0134 0.0018 -0.0289 0.0100 -0.0500 2.3402 0.1346 4.2500 4.2500 4.2645 0.0633 -0.0406 0.0857 16.1212 0.0115 0.0013 -0.0359 0.0003 -0.0542 2.3522 0.1008 4.2500 4.2500 4.3632 0.0321 -0.0503 0.0854 16.0433 0.0086 0.0008 -0.0468 -0.0156 -0.0606 2.3642 0.0527 4.2500 4.2500 4.7188 -0.0126 -0.0638 0.0852 15.9660 0.0045 0.0002 -0.0619 -0.0386 -0.0694 2.3750 0.0095 4.2500 4.2521 4.2521 -0.0529 -0.0757 0.0850 15.9048 0.0008 0.0000 -0.0757 0.0000 0.0000 RADIUS: 2.38 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.60 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.006127 TOTAL WEIGHT (Kg) = 0.002779 TOTAL VOLUME (IN**3) = 0.099821 TOTAL PROJECTED AREA (IN**2) = 1.6099 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000011 MOMENT OF INERTIA (Kg-M**2) = 0.000001 STATIC MOMENT, ONE SIDE (IN-LB) = 0.001897 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 99.096 INNER LIMIT (NORMALIZED BY RADIUS) = 0.105 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 32117.52 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.50, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.20, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412